Program uses method of characteristics for steady three-dimensional flow to calculate flow field in supersonic portion of mixed-compression aircraft inlet at non-zero angle of attack. Results agree well with experimental data except in regions of high viscous interaction. Flow field for variety of mixed-compression inlets can be calculated. Input includes geometry and attack of inlet. Output consists of list of parameters, solution planes, and description of shock waves. Program is written in FORTRAN IV for batch execution on CDC 6000-series.


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    Titel :

    Flow field in supersonic mixed-compression inlets


    Beteiligte:
    Bishop, A. R. (Autor:in) / Hoffman, J. D. (Autor:in) / Vadyak, J. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.08.1980



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Variable Geometry for Supersonic Mixed-Compression Inlets

    Norman E.Sorensen / Eldon A.Latham / Donald B. Smeltzer | AIAA | 1976


    Variable geometry for supersonic mixed-compression inlets

    SORENSEN, N. / LATHAM, E. / SMELTZER, D. | AIAA | 1974


    Variable geometry for supersonic mixed-compression inlets

    Sorensen, N. E. / Latham, E. A. / Smeltzer, D. B. | NTRS | 1974